期刊文献+
任意字段
题名或关键词
题名
关键词
文摘
作者
第一作者
机构
刊名
分类号
参考文献
作者简介
基金资助
栏目信息

针对机动目标的自适应滑模制导律研究 被引量：3

Research on Adaptive Sliding-mode Guidance Law Against Maneuvering Target
下载PDF
导出
摘要 针对机动目标,推导了自适应滑模制导律,并证明了自适应滑模制导律的有效性和鲁棒性。基于某型导弹对抗机动目标进行仿真计算,仿真结果表明针对机动目标的命中精度很高。 An approach to adaptive sliding-mode guidance law for missiles against maneuvering targets is deduced,and the effectiveness and robustness of this guidance law are verified.The simulation of missile against maneuvering targets is made.The simulation results show that the hitting accuracy against maneuvering targets is high.
作者 吴彤薇 钱磊 刘建淼
机构地区 中国空空导弹研究院
出处 《航空兵器》 2010年第1期16-19,共4页 Aero Weaponry
关键词 自适应滑模制导律 机动目标 鲁棒性 adaptive sliding-mode guidance law maneuvering target robustness
分类号 TJ765 [兵器科学与技术—武器系统与运用工程]
  • 相关文献

参考文献3

  • 1顾文锦,张乳川,于进勇.反舰导弹航向平面模糊滑模控制导引一体化研究[C]//2007中国控制与决策学术年会论文集,2007.
  • 2顾文锦,尚安利,李聪颖,袁玉满.基于二阶滑模控制的导弹自动驾驶仪设计[J].飞行力学,2004,22(4):29-32. 被引量：4
  • 3陈佳实,主编.导弹制导和控制系统的分析和设计[M].北京:宇航出版社,1989.

二级参考文献5

  • 1崔平远,郑建华,杨涤.具有频域指标约束的BTT导弹自动驾驶仪二次型法设计[J].宇航学报,1995,16(2):6-12. 被引量：8
  • 2钱杏芳 张鸿端 等.导弹飞行力学[M].北京:北京工业学院出版社,1987..
  • 3[1]Ryu J H,Tahk M J.Plant Inversion Control of Tail-Controlled Missiles[A].Proceedings of the AIAA Guidance,Navigation,and Control Conference[C]. New Orleans,Louisiana,1997.
  • 4[2]Bartolini G,Pisano A,Usai E.Global Stabilization of Nonlinear Uncertan Systems with Unmodelled Actuator Dynamics[J].IEEE Transactions on Automatic Control,2001,46(11):1 826-1 832.
  • 5[3]Bartolini G.Chattering Avoidance by Second-order Sliding Mode Control[J].IEEE Transactions on Automatic Control,1998,43(2):1 139-1 141.

共引文献9

同被引文献31

  • 1许佳骆,胥彪,冯建鑫,张金鹏.基于目标加速度方向观测的微分对策制导律[J].宇航总体技术,2021,5(1):27-36. 被引量：3
  • 2Morton B, Weininger N, Tiemo J E. Collective Manage- ment of Satellite Clusters [ C ]//AIAA Guidance, Naviga- tion and Control Conference, Portland, Oregon, 1999: 1576 - 1584.
  • 3Aorpimai M, Palmer P, Da Silva Curel A. Phase Acquisi- tion and Formation Keeping of a New Power Consumption Monitoring Satellite Constellation [ C ]//13th Annual AIAA/ USU Conference on Small Satellite, Logan, Utah, 1999.
  • 4Starin S R, Yedavalli R K, Sparks A G. Design of a LQR Controller of Reduced Inputs for Multiple Spacecraft For-mation Flying[ C ]//American Control Conference, 2001. Proceedings of the 2001, IEEE, 2001, 2:1327 - 1332.
  • 5Melton R G. Time-Explicit Representation of Relative Mo- tion between Elliptical Orbits [ J ]. Journal of Guidance, Control, and Dynamics, 2000, 23 (4) : 604 - 610.
  • 6Bainum P M, Tan Zhaozhi, Duma Xiaodong. Review of Station Keeping Strategies for Elliptieally Orbiting Constel- lations in Along -Track Formation [ J]. International Jour- nal of Solids mad Structures, 2005, 42(21/22) : 5683 - 5691.
  • 7Carter T E. State Transition Matrices for Terminal Rendez vous Studies : Brief Survey and New Example [ J ]. Journal of Guidance, Control, and Dynamics, 1998, 21 ( 1 ) : 148 - 155.
  • 8Ross I M. Linearized Dynamic Equations for Spacecraft Subject to J2 Perturbations [ J ]. Journal of Guidance, Con- trol, and Dynamics, 2003, 26 (4) : 657 -659.
  • 9Gim D W, Alfriend K T. The State Transition Matrix of Rela- tive Motion for Perturbed Non-Circular Reference Orbit [C]//Proceedings of the llth Annual AAS/AIAA Space Flight Mechanics Meeting, Santa Barbara, 2001 : 913 -934.
  • 10Alfriend K T, Yan Hui, Vadali S R. Nonlinear Considera- tions in Satellite Formation Flying[ C]//AIAA/AAS Astro- dynamics Specialist Conference and Exhibit, Monterey, CA, 2002.

引证文献3

二级引证文献9

航空兵器
2010年 第1期

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部